An experimental investigation into enhancing pulsejet performance through inlet redesign /
baseline inlet was defined as the inlet configuration
| Main Author: | |
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| Format: | Thesis eBook |
| Language: | English |
| Published: |
[Place of publication not identified] :
[publisher not identified] ;
1994.
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| Subjects: | |
| Online Access: | Link to OAKTrust copy |
| Summary: | baseline inlet was defined as the inlet configuration chamber during each combustion cycle. This larger air/fuel combustion chamber pressure measurements, inlet pressure combustion pressure produced more thrust for the pulsejet conditions and the performance characteristics for a static configuration successfully achieved the research objective. configuration was unsuccessful in achieving the research configuration. configurations respectively). The performance of these could not provide a large cross-sectional area of uniform, currently operated by hobbyists on their pulsejet engines. delivery of a larger air/fuel charge to the combustion diffusion and elevated the static pressure at the rear of the diffusion to the inlet geometry. In order to achieve this engine with the diffuser configuration. The cowl experimentally. Reed valve failure was more frequent and the goal, two different inlets were designed, constructed and inlet. The increased static pressure facilitated the inlets was evaluated relative to the baseline inlet. The internal and external diffusion (diffuser and cowl mass was responsible for the higher peak combustion chamber measurements and thrust measurements. The diffuser moving flow of air. The experimental data consisted of objective. The thrust and peak combustion chamber pressure of a small scale pulsejet through the introduction of pressure. Since the operational tests were conducted at a pulsejet engine never ran smoothly with the cowl relatively constant cycle frequency, the higher peak results were the lowest for the pulsejet with the cowl inlet. run do not correlate to a dynamic operation. In order to simulate a dynamic operation, the engine was tested in a steady flow. During engine operation, the large entrance for tested. These two inlets were designed using the concepts of The air supply system was a simple free jet of air, thus The consequences of this turbulent air were observed the cowl was ingesting a substantial amount of turbulent air. The diffuser inlet was designed with the concept of internal The objective of this research was to enhance the performance The pulsejet operates the most efficiently at static These poor results were attributed to the air supply system. |
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| Item Description: | "Major subject: Aerospace Engineering". Vita. |
| Physical Description: | xi, 83 leaves : illustrations ; 28 cm. Also available online. |
| Bibliography: | Includes bibliographical references. |